CN114602192B - Take aircraft of integral type installation element - Google Patents
Take aircraft of integral type installation element Download PDFInfo
- Publication number
- CN114602192B CN114602192B CN202210342426.XA CN202210342426A CN114602192B CN 114602192 B CN114602192 B CN 114602192B CN 202210342426 A CN202210342426 A CN 202210342426A CN 114602192 B CN114602192 B CN 114602192B
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- Prior art keywords
- battery module
- block
- aircraft
- groove
- supporting
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H29/00—Drive mechanisms for toys in general
- A63H29/22—Electric drives
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H29/00—Drive mechanisms for toys in general
- A63H29/24—Details or accessories for drive mechanisms, e.g. means for winding-up or starting toy engines
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- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses an aircraft with an integrated installation unit, which comprises an aircraft main body, wherein the bottom of the aircraft main body is provided with a battery module installation groove, a battery module is arranged in the battery module installation groove, sliding grooves are formed in the two sides of the battery module installation groove on the aircraft main body, traction plates are slidably clamped on the sliding grooves, the side surfaces of the traction plates are provided with limit frames, a supporting seat is arranged between the two traction plates, and an adjusting assembly convenient for buffering is arranged on the supporting seat; according to the battery module installation device, the installation unit of the aircraft can quickly install the battery module through the upward movement of the supporting seat and the matching between the limiting frame and the fixing assembly, meanwhile, the extrusion of the supporting seat triggers the abutting of the supporting assembly on the battery module, the installation stability of the battery module is ensured, the stability and the buffering effect of the installation unit of the battery module are ensured, and the battery module is prevented from being damaged.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft with an integrated installation unit.
Background
The appearance of aircraft toy usually adopts plane four-axis model, flies dish, helicopter row etc. and these aircraft toys mostly possess flight, shoot the function, and the accuracy, the flexibility of its function inclined to control more to and the discernment of aircraft to external environment. Battery module is as aircraft equipment's key part, be the power source of whole equipment, among the current battery module mounting structure, generally with in the battery module storehouse of battery module installation on the aircraft fuselage, and set up parts such as buckle in the battery module storehouse, and then fix battery module, but battery module and fuselage battery module storehouse fit clearance are big, not only striking and wearing and tearing appear easily at the flight in-process, when appearing dropping because of battery module to the power supply disconnection of aircraft simultaneously, cause the damage to aircraft battery module more easily, and the service environment of aircraft itself when the flight is relatively poor, battery module installation unit is insecure, lead to battery module to produce the damage, be unfavorable for the use of aircraft.
Disclosure of Invention
The invention aims to provide an aircraft with an integrated installation unit, wherein a supporting seat and a fixing component are arranged at the bottom of an aircraft main body, the installation unit of the aircraft can quickly install a battery module through the upward movement of the supporting seat and the matching between a limiting frame and the fixing component, meanwhile, the extrusion of the supporting seat triggers the abutting of the supporting component on the battery module, so that the installation stability of the battery module is ensured, in addition, when the aircraft drops, the swinging of the limiting component and an adjusting component triggers the limiting of a pull handle, the stability and the buffering effect of the installation unit of the battery module are further ensured, and the battery module is prevented from being damaged, so that the problems in the background technology are solved.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a take aircraft of integral type installation element, includes the aircraft main part, the battery module mounting groove has been seted up to the bottom of aircraft main part, be provided with battery module in the battery module mounting groove, the spout has all been seted up to the both sides that lie in the battery module mounting groove in the aircraft main part, the slip joint has the tractive board on the spout, the side of tractive board is provided with spacing frame, two be provided with the supporting seat between the tractive board, be provided with the adjusting part of the buffering of being convenient for on the supporting seat, the bottom both sides of aircraft main part all are provided with the fixed subassembly of being convenient for to adjust, the bottom both sides of supporting seat all are provided with the support frame, be provided with the spacing subassembly of being convenient for to trigger on the support frame, the both sides that lie in the battery module mounting groove in the aircraft main part are provided with the supporting component of being convenient for stable control.
Preferably, the spout is "L" type structure, the adjusting part includes the guide bar, the shifting chute has been seted up on the supporting seat, the guide bar is fixed to be pegged graft on the shifting chute, the movable block has been cup jointed in the slip on the guide bar, it has compression spring to lie in to cup joint between movable block and the shifting chute on the guide bar, the top of movable block articulates there is the connecting block, four the one end of connecting block articulates there is the contact plate.
Preferably, the guide rods are arranged in four groups, the four groups of guide rods are distributed on the supporting seat in a square shape, the moving block is in an L-shaped structure, the end part of the moving block extends to the outside of the traction plate, and the projection area of the contact plate is smaller than that of the battery module.
Preferably, fixed subassembly includes the fixing base, the operation groove has been seted up to the side of fixing base, it has the traction rod to slide to peg graft on the operation groove, the one end of traction rod is provided with the stopper, it has cup jointed first spring to lie in the operation groove on the traction rod, the other end of traction rod is provided with the pull handle.
Preferably, the end portions of the limiting blocks and the limiting frames are parallel and are in inclined plane structures, the end portions of the limiting blocks and the frame grooves of the limiting frames are matched and correspond to each other one by one, the pull handles are in frame-shaped structures, slots are formed in the bottoms of the pull handles, and the pull handles correspond to the end portions of the moving blocks one by one.
Preferably, the limiting assembly comprises a tubular air bag, an extrusion head is arranged at the other end of the tubular air bag, a clamping sliding groove is formed in the side face of the support frame, and a top block is inserted on the clamping sliding groove in a sliding mode.
Preferably, the tubular air bag is inserted in the bottom of the support frame in a sliding mode, the end portion of the tubular air bag extends to the outside of the support frame, the top block is of a T-shaped structure, and the end portion of the top block corresponds to the slot.
Preferably, the supporting component comprises a pressing block, the accommodating groove is formed in the two sides of the aircraft main body, which are located in the battery module mounting groove, the pressing block is of a T-shaped structure and is inserted into the accommodating groove in a sliding mode, the supporting block is inserted into the two sides of the accommodating groove in a sliding mode, the extrusion air bag is arranged between the supporting block and the pressing block, the supporting block is of an L-shaped structure, and a second spring is arranged between the supporting block and the accommodating groove.
Preferably, the end of the supporting block is provided with a groove, a fixed shaft is fixedly inserted in the groove, the fixed shaft is rotatably sleeved with the abutting blocks, a torsion spring is arranged on the fixed shaft between the abutting blocks, one end of the torsion spring is fixed on the fixed shaft, the other end of the torsion spring is fixed on the abutting blocks, and the end of the abutting blocks abuts against the bottom of the battery module.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the support seat and the fixing component are arranged at the bottom of the aircraft main body, the limit frame is matched with the fixing component through upward movement of the support seat, so that the battery module is rapidly installed by the installation unit of the aircraft, meanwhile, the support component is triggered to abut against the battery module through extrusion of the support seat, the stability of installation of the battery module is ensured, and in addition, when the aircraft falls, the limit component and the adjusting component are triggered to limit the pull handle through shaking, so that the stability and the buffering effect of the installation unit of the battery module are further ensured, the battery module is prevented from being damaged, and the aircraft is favorably used;
2. according to the aircraft battery module mounting structure, the aircraft main body is provided with the supporting component, the pressing block is triggered to upwards extrude to enable the supporting block to outwards move out of the supporting battery module while the mounting unit of the aircraft battery module is limited and fixed, the end part of the abutting block abuts against the bottom of the battery module under the action of the torsional force of the torsional spring, the stability of battery mounting is realized, and the phenomenon of collision caused by large fit clearance between the battery module and the aircraft battery module bin is avoided;
3. according to the invention, the limiting assembly is arranged on the supporting frame, when the aircraft falls off due to the power supply disconnection of the battery module, the ejecting block is triggered to eject upwards onto the slot, the pull handle is further limited, the mounting unit of the battery module is prevented from loosening, and the buffering effect and the protection performance of the battery module are improved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic bottom deployment view of the aircraft body of the present invention;
FIG. 3 is a schematic structural view of a battery mounting unit according to the present invention;
FIG. 4 is a sectional view of the mounting base of the present invention;
FIG. 5 is an enlarged schematic view of FIG. 5 at A according to the present invention;
FIG. 6 is a cross-sectional view of the aircraft body of the present invention;
FIG. 7 is an enlarged view of the structure of FIG. 7 at B according to the present invention;
FIG. 8 is a partial cross-sectional view of the support bracket of the present invention;
fig. 9 is an enlarged schematic view of the structure of fig. 8 at C according to the present invention.
In the figure: an aircraft body 1; a battery module mounting groove 2; a battery module 3; a chute 4; a drawplate 5; a limit frame 51; a support base 6; a guide rod 7; a moving block 71; a compression spring 72; a connecting block 73; a contact plate 74; a fixed seat 8; a pulling rod 81; a stop block 82; a first spring 83; a pull handle 84; a slot 85; a support frame 9; a tubular balloon 91; an extrusion head 92; a top block 93; briquetting 10; a support block 101; a squeeze balloon 102; a second spring 103; a fixed shaft 104; a resisting block 105; a torsion spring 106.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 9, the present invention provides a technical solution: the utility model provides a take aircraft of integral type installation element, including aircraft main part 1, battery module mounting groove 2 has been seted up to aircraft main part 1's bottom, battery module 3 has been held in battery module mounting groove 2, spout 4 has all been seted up to the both sides that lie in battery module mounting groove 2 in aircraft main part 1, spout 4 is "L" type structure, sliding clamping has drawplate 5 on spout 4, the side welding of drawplate 5 has spacing frame 51, be provided with supporting seat 6 between two drawplate 5, drawplate 5 and supporting seat 6 regard as battery module 3's installation element, drawplate 5 highly equals the degree of depth of spout 4, be convenient for the 6 laminating of supporting seat in aircraft main part 1's bottom.
Be provided with the adjusting part convenient to buffering on the supporting seat 6, the adjusting part includes guide bar 7, the shifting chute has been seted up on the supporting seat 6, guide bar 7 is fixed pegging graft on the shifting chute, guide bar 7 is provided with four groups, four groups of guide bar 7 are "kou" style of calligraphy and distribute on supporting seat 6, sliding sleeve has cup jointed movable block 71 on the guide bar 7, compression spring 72 has been cup jointed between movable block 71 and the shifting chute on the guide bar 7, movable block 71 is "L" type structure, and the tip extends to the outside of tractive board 5, the top of movable block 71 articulates there is connecting block 73, the one end of four connecting block 73 articulates there is contact plate 74, the top of contact plate 74 is rubber layer structure, the projected area of contact plate 73 is less than the projected area of battery module 3, when the supporting seat 6 upwards shifts up the laminating in the bottom of aircraft main part 1, under the effect of compression spring 72, promote movable block 71 to slide on guide bar 7, and then connecting block 73 removes promotion contact plate 74 laminating butt in the bottom of battery module 3, avoid battery module and fuselage battery module storehouse fit the clearance is big.
Both sides of the bottom of the aircraft body 1 are provided with fixed assemblies convenient to adjust, the fixed assemblies comprise a fixed base 8, an operation groove is formed in the side face of the fixed base 8, a traction rod 81 is inserted in the operation groove in a sliding mode, a limit block 82 is welded at one end of the traction rod 81, the end portion of the limit block 82 is parallel to the limit frame 51 and is of an inclined plane structure, the end portion of the limit block 82 is matched with the frame groove of the limit frame 51 one to one, a first spring 83 is sleeved in the operation groove on the traction rod 81, a pull handle 84 is welded at the other end of the traction rod 81, the pull handle 84 is of a frame structure, a slot 85 is formed in the bottom of the traction rod 84 and corresponds to the end portion of the moving block 71 one to one, when the aircraft drops due to the fact that the power supply of the battery module 3 is disconnected, the aircraft can shake the contact plate 74 up and down, the end portion of the moving block 71 extends into the frame of the pull handle 84 at one moment, limitation of the battery module 3 installation unit of the aircraft is achieved, and looseness of the battery module 3 is prevented.
The aircraft body 1 is provided with supporting components which are convenient for stable control and are arranged on two sides of the battery module mounting groove 2, each supporting component comprises a pressing block 10, accommodating grooves are formed in two sides of the aircraft body 1, which are positioned in the battery module mounting groove 2, the pressing blocks 10 are in a T-shaped structure and are inserted into the accommodating grooves in a sliding mode, supporting blocks 101 are inserted into two sides of the battery module mounting groove 2 in the accommodating grooves in a sliding mode, a squeezing air bag 102 is abutted between each supporting block 101 and the corresponding pressing block 10, each supporting block 101 is in an L-shaped structure, a second spring 103 is fixedly connected between each supporting block 101 and the corresponding accommodating groove, the end portions of the supporting blocks 101 are provided with grooves, fixing shafts 104 are fixedly inserted into the grooves, abutting blocks 105 are rotatably sleeved on the fixing shafts 104, and torsional springs 106 are sleeved between the abutting blocks 105 on the fixing shafts 104, one end of the torsion spring 106 is fixed on the fixing shaft 104, and the other end is fixed on the abutting block 105, the end of the abutting block 105 abuts against the bottom of the battery module 3, when the supporting seat 6 moves upwards and is attached to the bottom of the aircraft main body 1, in the process, the pressing block 10 is extruded at the top of the supporting seat 6 to move upwards, and then the pressing block 10 extrudes the extrusion air bag 102 at the top, so that the end gas of the extrusion air bag 102 is transmitted to the other end, the other end of the extrusion air bag 102 expands to extrude the supporting block 101 to move outwards to the accommodating groove to the battery module mounting groove 2, at the moment, under the action of the torsional force of the torsion spring 106, the abutting block 105 rotates around the fixing shaft 104 to abut against the bottom of the battery module 3, and the phenomenon that the collision occurs due to the large fit clearance between the battery module 3 and the battery module cabin of the aircraft body is avoided.
When the aircraft is in practical use, the battery module 3 is pushed upwards into the battery module mounting groove 2, the supporting seat 6 is pushed upwards, when the supporting seat 6 moves upwards, the inclined top surface of the limiting block 51 extrudes the inclined end surface of the limiting block 82, so that the end part of the limiting block 82 is pressed and accommodated into the operation groove, when the supporting seat 6 moves upwards and is attached to the bottom of the aircraft body 1, the end part of the limiting block 82 corresponds to the frame groove of the limiting block 51, under the elastic force of the first spring 83, the end part of the limiting block 82 is inserted into the frame groove of the limiting block 51, so that the limiting and fixing of the battery module mounting unit are realized, the rapid mounting of the battery module 3 is ensured, when the supporting seat 6 moves upwards and is attached to the bottom of the aircraft body 1, the moving block 71 is pushed to slide on the guide rod 7 under the elastic force of the compression spring 72, the connecting block 73 moves to push the contact plate 74 to be attached to the bottom of the battery module 3, in the process, the pressing block 10 moves upwards to press the airbag 102, so that the airbag 102 extrudes the airbag 102 to the airbag to move outwards to press the battery module mounting groove 101 to be matched with the battery module accommodating groove 104, and the torsion spring module, so that the battery module can be pressed against the torsion spring module 3 and the battery module can be pressed to be matched with the battery module 3 under the torsion spring 104; when the aircraft drops because of the power supply disconnection of battery module 3, can produce to rock contact plate 74 from top to bottom, the tip of movable block 71 extends to in the frame of pull handle 84 in an instant, realize spacing of the battery module 3 installation unit of aircraft, at first the tip of tubulose gasbag 91 touches ground and receives the extrusion simultaneously, on the one hand receive buffering effect to the installation unit of battery module 3, gaseous transmission to the head of extrusion head 92 of tip of tubulose gasbag 91 in this instant, the head inflation extrusion kicking block 93 of extrusion head 92 moves upwards, and then the tip of kicking block 93 is pegged graft on slot 85, on the other hand further carries on spacingly to pull handle 84, prevent that battery module 3's installation unit from appearing becoming flexible, avoid battery module to produce the damage, thereby be favorable to the use of aircraft.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (2)
1. An aircraft with an integrated installation unit, comprising an aircraft body, characterized in that: the aircraft comprises an aircraft body, and is characterized in that a battery module mounting groove is formed in the bottom of the aircraft body, battery modules are arranged in the battery module mounting groove, sliding grooves are formed in two sides of the aircraft body, which are positioned in the battery module mounting groove, pulling plates are connected to the sliding grooves in a sliding and clamping manner, a limiting frame is arranged on the side face of each pulling plate, a supporting seat is arranged between the two pulling plates, a regulating component convenient for buffering is arranged on the supporting seat, each sliding groove is of an L-shaped structure and comprises a guide rod, a moving groove is formed in the supporting seat, the guide rods are fixedly connected to the moving grooves in an inserting manner, moving blocks are connected to the guide rods in a sliding and sleeving manner, compression springs are connected to the guide rods between the moving blocks and the moving grooves in a sleeving manner, connecting blocks are hinged to the tops of the moving blocks, one ends of the four connecting blocks are hinged to contact plates, and when the supporting seat moves up and is attached to the bottom of the aircraft body, the contact plates are pushed to slide on the guide rods under the action of the elastic force of the compression springs, and then the connecting blocks move to push the contact plates to abut against the bottoms of the battery modules;
the aircraft comprises an aircraft body and is characterized in that fixing components convenient to adjust are arranged on two sides of the bottom of the aircraft body, each fixing component comprises a fixing seat, an operation groove is formed in the side face of each fixing seat, a traction rod is inserted in each operation groove in a sliding mode, a limiting block is arranged at one end of each traction rod, a first spring is sleeved on each traction rod and located in each operation groove, a pull handle is arranged at the other end of each traction rod, the end portions of the limiting blocks and the limiting frames are parallel and are in inclined plane structures, the end portions of the limiting blocks and the frame grooves of the limiting frames are matched and are in one-to-one correspondence, each pull handle is in a frame structure, a slot is formed in the bottom of each pull handle and the end portions of moving blocks are in one-to-one correspondence, supporting frames are arranged on two sides of the bottom of each supporting seat, the contact plates shake up and down, and the end portions of the moving blocks extend into the frames of the pull handles;
the support frame is provided with a limiting assembly convenient to trigger, the limiting assembly comprises a tubular air bag, the other end of the tubular air bag is provided with an extrusion head, the side face of the support frame is provided with a clamping sliding groove, the support frame is provided with a top block in sliding insertion connection on the clamping sliding groove, the tubular air bag is in sliding insertion connection with the bottom of the support frame, the end of the tubular air bag extends to the outside of the support frame, the top block is of a T-shaped structure, the end of the top block is arranged between the insertion grooves correspondingly, the end of the tubular air bag touches the ground and is extruded, the end gas of the tubular air bag is transmitted to the head of the extrusion head, the head of the extrusion head expands to extrude the top block to move upwards, and then the end of the top block is inserted on the insertion grooves;
the aircraft body is provided with support components convenient for stable control at two sides of the battery module mounting groove, each support component comprises a pressing block, the aircraft body is provided with accommodating grooves at two sides of the battery module mounting groove, each pressing block is of a T-shaped structure and is inserted into the accommodating groove in a sliding manner, supporting blocks are inserted into two sides of the battery module mounting groove in the accommodating groove in a sliding manner, an extrusion air bag is arranged between each supporting block and each pressing block, each supporting block is of an L-shaped structure, a second spring is arranged between each supporting block and the accommodating groove, the end part of each supporting block is provided with a groove, a fixed shaft is fixedly inserted into the groove, a supporting block is rotatably sleeved on the fixed shaft, a torsion spring is arranged between the supporting blocks on the fixed shaft, and one end of the torsion spring is fixed on the fixed shaft, and the other end is fixed on the abutting block, the end part of the abutting block abuts against the bottom of the battery module, under the action of the torsional force of the torsional spring, the abutting block rotates around the fixing shaft and abuts against the bottom of the battery module, when the supporting seat (6) moves upwards and is attached to the bottom of the aircraft main body (1), in the process, the top of the supporting seat (6) extrudes the pressing block (10) to move upwards, the top of the pressing block (10) extrudes the extrusion air bag (102), the end gas of the extrusion air bag (102) is transmitted to the other end, the other end of the extrusion air bag (102) expands to extrude the supporting block (101) to move outwards to the accommodating groove to the inside of the battery module mounting groove (2), and at the moment, under the action of the torsional force of the torsional spring (106), the abutting block (105) rotates around the fixing shaft (104) and abuts against the bottom of the battery module (3) And the phenomenon of collision caused by large fit clearance between the battery module (3) and the battery module bin of the machine body is avoided.
2. An aircraft with an integrated installation unit according to claim 1, characterized in that: the four groups of guide rods are distributed on the supporting seat in a square shape, the moving block is in an L-shaped structure, the end part of the moving block extends to the outside of the traction plate, and the projection area of the contact plate is smaller than that of the battery module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210342426.XA CN114602192B (en) | 2022-04-02 | 2022-04-02 | Take aircraft of integral type installation element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210342426.XA CN114602192B (en) | 2022-04-02 | 2022-04-02 | Take aircraft of integral type installation element |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114602192A CN114602192A (en) | 2022-06-10 |
| CN114602192B true CN114602192B (en) | 2022-12-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210342426.XA Active CN114602192B (en) | 2022-04-02 | 2022-04-02 | Take aircraft of integral type installation element |
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| CN (1) | CN114602192B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115138081A (en) * | 2022-08-01 | 2022-10-04 | 董群法 | Children toy |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585547A (en) * | 2017-10-17 | 2018-01-16 | 安徽安凯汽车股份有限公司 | A kind of carrierless formula high-tension battery mounting tool |
| WO2018024086A1 (en) * | 2016-08-01 | 2018-02-08 | 亿航智能设备（广州）有限公司 | Battery and aircraft |
| WO2018195786A1 (en) * | 2017-04-26 | 2018-11-01 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN212587638U (en) * | 2020-06-05 | 2021-02-23 | 武汉青绿山水科技有限公司 | Battery fixing structure for unmanned aerial vehicle |
| CN113517508A (en) * | 2021-03-15 | 2021-10-19 | 保信科技(杭州)有限公司 | New energy battery box with multi-level buffer function |
| CN215731999U (en) * | 2021-09-25 | 2022-02-01 | 深圳市骑豹新能源科技有限公司 | General aircraft battery bracket component |
-
2022
- 2022-04-02 CN CN202210342426.XA patent/CN114602192B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018024086A1 (en) * | 2016-08-01 | 2018-02-08 | 亿航智能设备（广州）有限公司 | Battery and aircraft |
| WO2018195786A1 (en) * | 2017-04-26 | 2018-11-01 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN107585547A (en) * | 2017-10-17 | 2018-01-16 | 安徽安凯汽车股份有限公司 | A kind of carrierless formula high-tension battery mounting tool |
| CN212587638U (en) * | 2020-06-05 | 2021-02-23 | 武汉青绿山水科技有限公司 | Battery fixing structure for unmanned aerial vehicle |
| CN113517508A (en) * | 2021-03-15 | 2021-10-19 | 保信科技(杭州)有限公司 | New energy battery box with multi-level buffer function |
| CN215731999U (en) * | 2021-09-25 | 2022-02-01 | 深圳市骑豹新能源科技有限公司 | General aircraft battery bracket component |
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| Publication number | Publication date |
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| CN114602192A (en) | 2022-06-10 |
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